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N-14 (n14-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: N-14 (n14-il)
Reynolds number: 100,000
Max Cl/Cd: 40.54 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n14-il-100000.txt
Download as CSV file: xf-n14-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-14                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.8386   0.07009   0.06409  -0.0434   1.0000   0.0821
 -10.750  -0.8558   0.06631   0.06020  -0.0402   1.0000   0.0819
 -10.500  -0.8666   0.06236   0.05613  -0.0375   1.0000   0.0815
 -10.250  -0.8786   0.05868   0.05227  -0.0342   1.0000   0.0813
 -10.000  -0.8883   0.05508   0.04845  -0.0307   1.0000   0.0809
  -9.750  -0.8963   0.05161   0.04471  -0.0270   1.0000   0.0807
  -9.500  -0.9015   0.04833   0.04112  -0.0232   1.0000   0.0806
  -9.250  -0.9054   0.04548   0.03788  -0.0191   1.0000   0.0811
  -9.000  -0.9075   0.04312   0.03505  -0.0148   1.0000   0.0819
  -8.750  -0.8990   0.04013   0.03194  -0.0125   1.0000   0.0835
  -8.500  -0.8861   0.03811   0.02983  -0.0104   1.0000   0.0852
  -8.250  -0.8740   0.03613   0.02763  -0.0080   1.0000   0.0866
  -8.000  -0.8614   0.03443   0.02570  -0.0055   1.0000   0.0889
  -7.750  -0.8492   0.03291   0.02386  -0.0028   1.0000   0.0918
  -7.500  -0.8366   0.03150   0.02206   0.0001   1.0000   0.0941
  -7.250  -0.8173   0.02941   0.01989   0.0015   1.0000   0.0967
  -7.000  -0.7982   0.02806   0.01850   0.0029   1.0000   0.1003
  -6.750  -0.7807   0.02699   0.01728   0.0049   1.0000   0.1054
  -6.500  -0.7609   0.02559   0.01575   0.0064   1.0000   0.1106
  -6.250  -0.7409   0.02433   0.01458   0.0078   1.0000   0.1173
  -6.000  -0.7216   0.02303   0.01324   0.0094   1.0000   0.1262
  -5.750  -0.7054   0.02184   0.01217   0.0115   1.0000   0.1405
  -5.500  -0.6923   0.02069   0.01126   0.0140   1.0000   0.1618
  -5.250  -0.6804   0.01979   0.01055   0.0168   1.0000   0.1897
  -5.000  -0.6668   0.01920   0.01005   0.0193   1.0000   0.2156
  -4.750  -0.6525   0.01869   0.00964   0.0217   1.0000   0.2405
  -4.500  -0.6385   0.01815   0.00927   0.0240   1.0000   0.2678
  -4.250  -0.6250   0.01757   0.00890   0.0265   1.0000   0.3067
  -4.000  -0.6139   0.01681   0.00853   0.0294   1.0000   0.3623
  -3.750  -0.6046   0.01602   0.00826   0.0328   1.0000   0.4420
  -3.500  -0.5961   0.01529   0.00821   0.0368   1.0000   0.5527
  -3.250  -0.5819   0.01497   0.00848   0.0404   1.0000   0.6709
  -3.000  -0.5618   0.01510   0.00885   0.0430   1.0000   0.7542
  -2.750  -0.5368   0.01542   0.00919   0.0446   1.0000   0.8088
  -2.500  -0.5055   0.01587   0.00960   0.0449   1.0000   0.8500
  -2.250  -0.4660   0.01647   0.01009   0.0436   1.0000   0.8812
  -2.000  -0.4120   0.01731   0.01079   0.0395   1.0000   0.9054
  -1.750  -0.3544   0.01814   0.01146   0.0344   1.0000   0.9257
  -1.500  -0.2897   0.01891   0.01209   0.0278   1.0000   0.9413
  -1.250  -0.2270   0.01944   0.01248   0.0211   1.0000   0.9550
  -1.000  -0.1635   0.01985   0.01280   0.0140   1.0000   0.9701
  -0.750  -0.0895   0.02005   0.01292   0.0047   1.0000   0.9843
  -0.500  -0.0090   0.02000   0.01282  -0.0060   1.0000   0.9991
  -0.250  -0.0053   0.01997   0.01278  -0.0034   1.0000   1.0000
   0.000  -0.0072   0.01997   0.01276   0.0002   1.0000   1.0000
   0.250  -0.0089   0.01998   0.01277   0.0038   1.0000   1.0000
   0.500   0.0358   0.02007   0.01288  -0.0008   0.9921   1.0000
   0.750   0.0919   0.02014   0.01298  -0.0072   0.9813   1.0000
   1.000   0.1487   0.02012   0.01301  -0.0136   0.9704   1.0000
   1.250   0.2013   0.01994   0.01290  -0.0190   0.9577   1.0000
   1.750   0.3140   0.01918   0.01236  -0.0301   0.9297   1.0000
   2.000   0.4029   0.01792   0.01129  -0.0404   0.9122   1.0000
   2.250   0.4623   0.01689   0.01040  -0.0452   0.8873   1.0000
   2.500   0.5120   0.01611   0.00975  -0.0483   0.8609   1.0000
   2.750   0.5461   0.01557   0.00925  -0.0483   0.8226   1.0000
   3.000   0.5718   0.01520   0.00884  -0.0467   0.7730   1.0000
   3.250   0.5904   0.01500   0.00853  -0.0438   0.7094   1.0000
   3.500   0.6079   0.01501   0.00821  -0.0408   0.6284   1.0000
   3.750   0.6223   0.01535   0.00812  -0.0377   0.5479   1.0000
   4.000   0.6350   0.01583   0.00822  -0.0346   0.4812   1.0000
   4.250   0.6479   0.01634   0.00843  -0.0317   0.4276   1.0000
   4.500   0.6610   0.01689   0.00873  -0.0290   0.3824   1.0000
   4.750   0.6734   0.01748   0.00908  -0.0262   0.3393   1.0000
   5.000   0.6853   0.01806   0.00948  -0.0233   0.2931   1.0000
   5.250   0.6958   0.01870   0.00989  -0.0202   0.2420   1.0000
   5.500   0.7051   0.01961   0.01046  -0.0169   0.1933   1.0000
   5.750   0.7159   0.02072   0.01128  -0.0139   0.1635   1.0000
   6.000   0.7298   0.02174   0.01216  -0.0114   0.1460   1.0000
   6.250   0.7465   0.02284   0.01317  -0.0094   0.1352   1.0000
   6.500   0.7643   0.02384   0.01408  -0.0076   0.1262   1.0000
   6.750   0.7832   0.02494   0.01526  -0.0059   0.1188   1.0000
   7.000   0.8029   0.02604   0.01635  -0.0044   0.1129   1.0000
   7.250   0.8235   0.02752   0.01786  -0.0031   0.1079   1.0000
   7.500   0.8406   0.02861   0.01917  -0.0010   0.1027   1.0000
   7.750   0.8595   0.02995   0.02054   0.0005   0.0987   1.0000
   8.000   0.8773   0.03186   0.02256   0.0021   0.0950   1.0000
   8.250   0.8894   0.03326   0.02432   0.0049   0.0914   1.0000
   8.500   0.9031   0.03500   0.02632   0.0073   0.0888   1.0000
   8.750   0.9181   0.03661   0.02799   0.0093   0.0857   1.0000
   9.000   0.9297   0.03924   0.03073   0.0113   0.0832   1.0000
   9.250   0.9312   0.04140   0.03338   0.0154   0.0817   1.0000
   9.500   0.9310   0.04412   0.03652   0.0194   0.0807   1.0000
   9.750   0.9271   0.04694   0.03974   0.0235   0.0798   1.0000
  10.000   0.9195   0.04988   0.04302   0.0277   0.0788   1.0000
  10.250   0.9079   0.05301   0.04645   0.0320   0.0783   1.0000
  10.500   0.8911   0.05627   0.04997   0.0364   0.0780   1.0000
  10.750   0.8672   0.05966   0.05359   0.0410   0.0785   1.0000
  11.000   0.8396   0.06312   0.05721   0.0453   0.0794   1.0000
  11.250   0.8091   0.06727   0.06150   0.0476   0.0802   1.0000
  11.500   0.7823   0.07215   0.06650   0.0479   0.0813   1.0000
  11.750   0.7619   0.07756   0.07196   0.0468   0.0823   1.0000
  12.000   0.7567   0.08291   0.07731   0.0462   0.0833   1.0000
  12.250   0.6255   0.12669   0.12116   0.0186   0.1537   1.0000
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